Review on Cryogenic and Jet Engine
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Different Types of Rocket Nozzles
Different Types of Rocket Nozzles 5322- Rocket Propulsion Project Report By Patel Harinkumar Rajendrabhai(1001150586) 1. Introduction 1.1 What is Nozzle and why they are used? A nozzle is a device designed to control the direction or characteristics of a fluid flow (especially to increase velocity) as it exits (or enters) an enclosed chamber or Pipe[9]. Nozzles are frequently used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that emerges from them. In nozzle velocity of fluid increases on the expense of its pressure energy. A Water Nozzle[9] Rotator Style Pivot Sprinkler[9] 1.2 What is Rocket Nozzle? A rocket engine nozzle is a propelling nozzle (usually of the de Laval type) used in a rocket engine to expand and accelerate the hot gases from combustion so as to produce thrust according to Newton’s law of motion. Combustion gases are produced by burning the propellants in combustor, they exit the nozzle at very high Speed (hypersonic). 1.3 Properties of Rocket Nozzle Nozzle produces thrust. Exhaust gases from combustion are pushed into throat region of nozzle. Throat is smaller cross-sectional area than rest of engine, gases are compressed to high pressure. Nozzle gradually increases in cross-sectional area allowing gases to expand and push against walls creating thrust. Convert thermal energy of hot chamber gases into kinetic energy and direct that energy along nozzle axis.[1] Mathematically, ultimate purpose of nozzle is to expand gases as efficiently as possible so as to maximize exit velocity.[1] Rocket Engine[1] F m eVe Pe Pa Ae Neglecting Pressure losses F m eVe 2 Different types of Rocket Nozzle Configuration(shape) The rocket nozzles can have many shapes configurations. -
Safety Consideration on Liquid Hydrogen
Safety Considerations on Liquid Hydrogen Karl Verfondern Helmholtz-Gemeinschaft der 5/JULICH Mitglied FORSCHUNGSZENTRUM TABLE OF CONTENTS 1. INTRODUCTION....................................................................................................................................1 2. PROPERTIES OF LIQUID HYDROGEN..........................................................................................3 2.1. Physical and Chemical Characteristics..............................................................................................3 2.1.1. Physical Properties ......................................................................................................................3 2.1.2. Chemical Properties ....................................................................................................................7 2.2. Influence of Cryogenic Hydrogen on Materials..............................................................................9 2.3. Physiological Problems in Connection with Liquid Hydrogen ....................................................10 3. PRODUCTION OF LIQUID HYDROGEN AND SLUSH HYDROGEN................................... 13 3.1. Liquid Hydrogen Production Methods ............................................................................................ 13 3.1.1. Energy Requirement .................................................................................................................. 13 3.1.2. Linde Hampson Process ............................................................................................................15 -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
2. Afterburners
2. AFTERBURNERS 2.1 Introduction The simple gas turbine cycle can be designed to have good performance characteristics at a particular operating or design point. However, a particu lar engine does not have the capability of producing a good performance for large ranges of thrust, an inflexibility that can lead to problems when the flight program for a particular vehicle is considered. For example, many airplanes require a larger thrust during takeoff and acceleration than they do at a cruise condition. Thus, if the engine is sized for takeoff and has its design point at this condition, the engine will be too large at cruise. The vehicle performance will be penalized at cruise for the poor off-design point operation of the engine components and for the larger weight of the engine. Similar problems arise when supersonic cruise vehicles are considered. The afterburning gas turbine cycle was an early attempt to avoid some of these problems. Afterburners or augmentation devices were first added to aircraft gas turbine engines to increase their thrust during takeoff or brief periods of acceleration and supersonic flight. The devices make use of the fact that, in a gas turbine engine, the maximum gas temperature at the turbine inlet is limited by structural considerations to values less than half the adiabatic flame temperature at the stoichiometric fuel-air ratio. As a result, the gas leaving the turbine contains most of its original concentration of oxygen. This oxygen can be burned with additional fuel in a secondary combustion chamber located downstream of the turbine where temperature constraints are relaxed. -
Cryogenic Technology & Rocket Engines
ISSN (O): 2393-8609 International Journal of Aerospace and Mechanical Engineering Volume 2 – No.5, August 2015 Cryogenic Technology & Rocket Engines AKHIL GARG KARTIK JAKHU KISHAN SINGH ABHINAV B.Tech – Aerospace B.Tech – Aerospace B.Tech – Aerospace MAURYA Engg. Engg. Engg. B.Tech – Aerospace PUNJAB PUNJAB PUNJAB Engg. TECHNICAL TECHNICAL TECHNICAL PUNJAB UNIVERSITY, UNIVERSITY, UNIVERSITY, TECHNICAL JALANDHAR JALANDHAR JALANDHAR UNIVERSITY, akhilgarg.313@g kartik.lphawk@g kishansngh1996 JALANDHAR mail.com mail.com @gmail.com abhinavguru123 @gmail.com ABSTRACT 3.2 What is Cryogenic Rocket Engine? This paper is all about the rocket engine involving the use of A cryogenic rocket engine is a rocket engine that cryogenic technology at a cryogenic temperature (123K). This uses a cryogenic fuel or oxidizer, that is, its fuel or basically uses the liquid oxygen and liquid hydrogen as an oxidizer (or both) is gases liquefied and stored at oxidizer and fuel, which are very clean and non-pollutant very low temperatures. Notably, these engines were fuels compared to other hydrocarbon fuels like petrol, diesel, one of the main factors of the ultimate success in gasoline, LPG, CNG, etc., sometimes, liquid nitrogen is also reaching the Moon by the Saturn V rocket. used as an fuel. During World War II, when powerful rocket engines were first considered by the German, American and Keywords Soviet engineers independently, all discovered that Rocket engine, Cryogenic technology, Cryogenic temperature, rocket engines need high mass flow rate of both Liquid hydrogen and Oxygen. oxidizer and fuel to generate a sufficient thrust. At that time oxygen and low molecular weight 1. -
Reaction Engines and High-Speed Propulsion
Reaction Engines and High-Speed Propulsion Future In-Space Operations Seminar – August 7, 2019 Adam F. Dissel, Ph.D. President, Reaction Engines Inc. 1 Copyright © 2019 Reaction Engines Inc. After 60 years of Space Access…. Copyright © 2019 Reaction Engines Inc. …Some amazing things have been achieved Tangible benefits to everyday life Expansion of our understanding 3 Copyright © 2019 Reaction Engines Inc. Accessing Space – The Rocket Launch Vehicle The rocket launch vehicle (LV) has carried us far…however current launchers still remain: • Expensive • Low-Operability • Low-Reliability …Which increases the cost of space assets themselves and restricts growth of space market …little change in launch vehicle technology in almost 60 years… 1957 Today 4 Copyright © 2019 Reaction Engines Inc. Why All-Rocket LV’s Could Use Help All-rocket launch vehicles (LVs) are challenged by the physics that dictate performance thresholds…little improvement in key performance metrics have been for decades Mass Fraction Propulsion Efficiency – LH2 Example Reliability 1400000 Stage 2 Propellant 500 1.000 Propellent 450 1200000 Vehicle Structure 0.950 236997 400 1000000 350 0.900 300 800000 0.850 250 Launches 0.800 600000 320863 200 906099 150 400000 Orbital Successful 0.750 100 Hydrogen Vehicle Weights (lbs) Weights Vehicle 0.700 LV Reliability 454137 (seconds)Impulse 200000 50 Rocket Engines Hydrogen Rocket Specific Specific Rocket Hydrogen 0 0.650 0 48943 Falcon 9 777-300ER 1950 1960 1970 1980 1990 2000 2010 2020 1950 1960 1970 1980 1990 2000 2010 2020 Air-breathing enables systems with increased Engine efficiency is paramount but rocket Launch vehicle reliability has reached a plateau mass margin which yields high operability, technology has not achieved a breakthrough in and is still too low to support our vision of the reusability, and affordability decades future in space 5 Copyright © 2019 Reaction Engines Inc. -
Chap21 Rockets Fundamentals.Pdf
Chapter 21.indd 449 1/9/08 12:12:24 PM There is an explanation for everything that a rocket does. The explanation is most always based on the laws of physics and the nature of rocket propellants. Experimentation is required to find out whether a new rocket will or will not work. Even today, with all the knowledge and expertise that exists in the field of rocketry, experimentation occasionally shows that certain ideas are not practical. In this chapter, we will look back in time to the early developers and users of rocketry. We will review some of the physical laws that apply to rocketry, discuss selected chemicals and their combinations, and identify the rocket systems and their components. We also will look at the basics of rocket propellant efficiency. bjectives Explain why a rocket engine is called a reaction engine. Identify the country that first used the rocket as a weapon. Compare the rocketry advancements made by Eichstadt, Congreve and Hale. Name the scientist who solved theoretically the means by which a rocket could escape the earth’s gravitational field. Describe the primary innovation in rocketry developed by Dr. Goddard and Dr. Oberth. Explain the difference between gravitation and gravity. Describe the contributions of Galileo and Newton. Explain Newton’s law of universal gravitation. State Newton’s three laws of motion. Define force, velocity, acceleration and momentum. Apply Newton’s three laws of motion to rocketry. Identify two ways to increase the thrust of a rocket. State the function of the combustion chamber, the throat, and nozzle in a rocket engine. -
Turbojet Runs Precursor to Hypersonic Engine Heat Exchanger Tests
Turbojet Runs Precursor to Hypersonic Engine Heat Exchanger Tests Aviation Week & Space Technology Guy Norris Tue, 2018-05-15 04:00 Advanced propulsion developer Reaction Engines is nearing its first step toward validating its novel air-breathing hybrid rocket design at hypersonic conditions by firing up a vintage General Electric J79 turbojet to act as a heat source for testing, expected later this month. The ex-military engine, formerly used in a McDonnell Douglas F-4, is a central element of Reaction’s specially developed high-temperature airflow test site, which will soon be commissioned at Front Range Airport, near Watkins, Colorado. The J79 will provide heated gas flow in excess of 1,000C (1,800F) which, together with conditioned ambient air, will be mixed to replicate inlet conditions representative of flight speeds up to and including Mach 5. The flow will verify the operability and performance of the pre-cooler heat exchanger (HTX), which is at the core of Reaction’s Sabre (synergistic air-breathing rocket engine). It is also key to extracting oxygen from the atmosphere to enable acceleration to hypersonic speed from a standing start. The HTX will chill airflow to minus 150C in less than 1/20th of a second, and pass it through a turbo- compressor and into the rocket combustion chamber where it will be burned with sub-cooled liquid hydrogen (LH) fuel. Beyond Mach 5, and at an altitude approaching 100,000 ft. the inlet will be closed and the engine will continue to operate as a closed-cycle rocket engine fueled by onboard liquid oxygen and LH. -
Design of a Rocket- Based Combined Cycle Engine
Design of a Rocket- Based Combined Cycle Engine A project present to The Faculty of the Department of Aerospace Engineering San Jose State University in partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering By Andrew Munoz May 2011 approved by Dr. Periklis Papadopoulos Faculty Advisor © 2011 Andrew Munoz ALL RIGHTS RESERVED 2 3 DESIGN OF A ROCKET-BASED COMBINED CYCLE ENGINE by Andrew Munoz A BST R A C T Current expendable space launch vehicles using conventional all-rocket propulsion systems have virtually reached their performance limits with respect to payload capacity. A promising approach to increase payload capacity and to provide reusability is to utilize airbreathing propulsion systems for a portion of the flight to reduce oxidizer weight and potentially increase payload and structural capacity. A Rocket-Based Combined Cycle (RBCC) engine would be capable of providing transatmospheric flight while increasing propulsion performance by utilizing a rocket integrated airbreathing propulsion system. An analytical model of a Rocket-Based Combined Cycle (RBCC) engine was developed using the stream thrust method as a solution to the governing equations of aerothermodynamics. This analytical model provided the means for calculating the propulsion performance of an ideal RBCC engine over the airbreathing flight regime (Mach 0 to 12) as well as a means of comparison with conventional rocket propulsion systems. The model was developed by choosing the highest performance propulsion cycles for a given flight regime and then integrating them into a single engine which would utilize the same components (inlet, rocket, combustor, and nozzle) throughout the entire airbreathing flight regime. -
Space Shuttle Main Engine Orientation
BC98-04 Space Transportation System Training Data Space Shuttle Main Engine Orientation June 1998 Use this data for training purposes only Rocketdyne Propulsion & Power BOEING PROPRIETARY FORWARD This manual is the supporting handout material to a lecture presentation on the Space Shuttle Main Engine called the Abbreviated SSME Orientation Course. This course is a technically oriented discussion of the SSME, designed for personnel at any level who support SSME activities directly or indirectly. This manual is updated and improved as necessary by Betty McLaughlin. To request copies, or obtain information on classes, call Lori Circle at Rocketdyne (818) 586-2213 BOEING PROPRIETARY 1684-1a.ppt i BOEING PROPRIETARY TABLE OF CONTENT Acronyms and Abbreviations............................. v Low-Pressure Fuel Turbopump............................ 56 Shuttle Propulsion System................................. 2 HPOTP Pump Section............................................ 60 SSME Introduction............................................... 4 HPOTP Turbine Section......................................... 62 SSME Highlights................................................... 6 HPOTP Shaft Seals................................................. 64 Gimbal Bearing.................................................... 10 HPFTP Pump Section............................................ 68 Flexible Joints...................................................... 14 HPFTP Turbine Section......................................... 70 Powerhead........................................................... -
Supersonic Combustion Ramjet: Analysis on Fuel Options
SUPERSONIC COMBUSTION RAMJET: ANALYSIS ON FUEL OPTIONS by Stephanie W. Barone A thesis submitted to the faculty of The University of Mississippi in partial fulfillment of the requirements of the Sally McDonnell Barksdale Honors College. Oxford May 2004 Approved by ___________________________________ Advisor: Dr. Jeffrey Roux ___________________________________ Reader: Dr. Erik Hurlen ___________________________________ Reader: Dr. John O’Haver 1 © 2016 STEPHANIE BARONE ALL RIGHTS RESERVED 2 ABSTRACT STEPHANIE BARONE: Supersonic Combustion Ramjet: Analysis on Fuel Options This report focuses on different fuel options available to use for scramjet engines. The advantages and disadvantages of JP-7, JP-8, and hydrogen fuels are covered, also the effectiveness and requirements for each fuel are discussed. The recent history of the scramjet engine is included as well as its advantages and disadvantages. An explanation of what each fuel option encompasses and engineering analysis for each fuel are shown. The equations presented for the parametric analysis are shown as functions of the freestream Mach number, with the combustion Mach number as a parameter. The results can be seen for the theoretical possibilities of the scramjet engine and the most likely operating situations. Hydrogen has the highest lower heating value which makes it very appealing to use as a fuel, but it is not very dense so more volume of it is needed to create enough energy. The hydrocarbon fuels, JP-7 and JP-8, have half the value of hydrogen for the lower heating value -
Extensions to the Time Lag Models for Practical Application to Rocket
The Pennsylvania State University The Graduate School College of Engineering EXTENSIONS TO THE TIME LAG MODELS FOR PRACTICAL APPLICATION TO ROCKET ENGINE STABILITY DESIGN A Dissertation in Mechanical Engineering by Matthew J. Casiano © 2010 Matthew J. Casiano Submitted in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy August 2010 The dissertation of Matthew J. Casiano was reviewed and approved* by the following: Domenic A. Santavicca Professor of Mechanical Engineering Co-chair of Committee Vigor Yang Adjunct Professor of Mechanical Engineering Dissertation Advisor Co-chair of Committee Richard A. Yetter Professor of Mechanical Engineering André L. Boehman Professor of Fuel Science and Materials Science and Engineering Tomas E. Nesman Aerospace Engineer at NASA Marshall Space Flight Center Special Member Karen A. Thole Professor of Aerospace Engineering Head of the Department of Mechanical and Nuclear Engineering *Signatures are on file in the Graduate School iii ABSTRACT The combustion instability problem in liquid-propellant rocket engines (LREs) has remained a tremendous challenge since their discovery in the 1930s. Improvements are usually made in solving the combustion instability problem primarily using computational fluid dynamics (CFD) and also by testing demonstrator engines. Another approach is to use analytical models. Analytical models can be used such that design, redesign, or improvement of an engine system is feasible in a relatively short period of time. Improvements to the analytical models can greatly aid in design efforts. A thorough literature review is first conducted on liquid-propellant rocket engine (LRE) throttling. Throttling is usually studied in terms of vehicle descent or ballistic missile control however there are many other cases where throttling is important.